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首先在二体意义下采用粒子群优化算法(PSO)求解Lambert问题,确定发射窗口和二体地火转移轨道。使用圆锥曲线拼接法设计地心停泊轨道、逃逸轨道,并作为轨道精确设计的初值,以建立在火星的B平面参数和地火转移时间为约束,在精确动力学模型下进行微分迭代修正,最终得到满足约束的精确轨道。将设计轨道在STK软件中仿真,结果吻合。
Firstly, particle swarm optimization (PSO) is used to solve the Lambert problem in the sense of two bodies, and the fire-transfer orbit between the launch window and the body is determined. The concentric curved stitching method is used to design the orbital mooring orbit of the earth’s center and to serve as the initial value of accurate orbit design. The B-plane parameter and ground-fire transfer time of Mars are constrained, and the differential iterative correction is performed under the accurate dynamic model. Finally get the exact trajectory to meet the constraints. The design track in STK simulation software, the results match.